U.S. patent application number 15/154906 was filed with the patent office on 2017-11-16 for retractable wheel assembly.
The applicant listed for this patent is Luis Sierra. Invention is credited to Luis Sierra.
Application Number | 20170327207 15/154906 |
Document ID | / |
Family ID | 60294748 |
Filed Date | 2017-11-16 |
United States Patent
Application |
20170327207 |
Kind Code |
A1 |
Sierra; Luis |
November 16, 2017 |
RETRACTABLE WHEEL ASSEMBLY
Abstract
A retractable wheel assembly includes arm assemblies, wheels, a
retraction arm, and a threaded shaft. The arm assemblies are
hingedly attached to a lower frame of a utility vehicle. Each arm
assembly comprises a first arm, a second arm, and a third arm
hingedly linked there between. Each wheel is connected to the third
arm of each arm assembly. The retraction arm is connected to the
second arm, and a threaded shaft. The threaded shaft is configured
to be actuated rearwardly where the retraction arm is rearwardly
pulled causing the second arm to unfold the arm assembly outwardly
and deploy the wheels and for motion of the utility vehicle. Then,
the threaded shaft is configured to be actuated forwardly where the
retraction arm is pushed forward causing the second arm to fold the
arm assembly inwardly and fold the wheels and when the utility
vehicle is positioned at rest.
Inventors: |
Sierra; Luis; (London,
CA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Sierra; Luis |
London |
|
CA |
|
|
Family ID: |
60294748 |
Appl. No.: |
15/154906 |
Filed: |
May 13, 2016 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64C 25/12 20130101;
B60G 2204/47 20130101; B64C 25/20 20130101; B62D 63/062 20130101;
B60G 3/20 20130101; B60G 2300/04 20130101; B62D 63/061
20130101 |
International
Class: |
B64C 25/20 20060101
B64C025/20; B62D 63/06 20060101 B62D063/06; B62D 63/06 20060101
B62D063/06; B64C 25/12 20060101 B64C025/12 |
Claims
1. A retractable wheel assembly, comprising: at least two arm
assemblies hingedly attached to a lower frame of a utility vehicle,
and symmetrically disposed along the lower frame, each arm assembly
comprising; a first arm hingedly connected to the lower frame; a
second arm hingedly linked to the first arm; and a third arm
hingedly linked to the second arm; a pair of wheels, wherein each
wheel is hingedly connected at distal ends of the third arm of each
arm assembly, and hingedly connected to the lower frame; a
retraction arm hingedly connected to the second arm, and a distal
end of the retraction arm in hinged connection with an end of a
threaded shaft, wherein the threaded shaft is centrally positioned
between the two arm assemblies and perpendicular to the arm
assemblies; the threaded shaft configured to be actuated in a
rearward movement where the retraction arm is rearwardly pulled
causing the second arm to unfold the arm assembly outwardly and
deploy the wheels for motion of the utility vehicle, and further
wherein the threaded shaft is configured to be actuated in a
forward movement, where the retraction arm is pushed forward
causing the second arm to fold the arm assembly inwardly and fold
the wheels when the utility vehicle is positioned at rest.
2. A retractable wheel assembly for an aircraft, comprising: at
least two arm assemblies hingedly attached to a lower frame of the
aircraft, and symmetrically disposed along the lower frame, each
arm assembly comprising; a first arm hingedly connected to the
lower frame; a second arm hingedly linked to the first arm; and a
third arm hingedly linked to the second arm; a pair of wheels,
wherein each wheel is hingedly connected at distal ends of the
third arm of each arm assembly, and hingedly connected to the lower
frame; a retraction arm hingedly connected to the second arm, and a
distal end of the retraction arm in hinged connection with an end
of a threaded shaft, wherein the threaded shaft is centrally
positioned between the two arm assemblies and perpendicular to the
arm assemblies; the threaded shaft configured to be actuated in a
rearward movement where the retraction arm is rearwardly pulled
causing the second arm to unfold the arm assembly outwardly to
deploy the wheels for landing of the aircraft, and further wherein
the threaded shaft is configured to be actuated in a forward
movement where the retraction arm is pushed forward causing the
second arm to fold the arm assembly inwardly to fold the wheels
during takeoff of the aircraft.
3. The retractable wheel assembly of claim 2, wherein the wheels
are configured to be extended across a predefined span via radially
extending the arm assembly, wherein the predefined extension of the
wheels stabilizes the landing of the aircraft.
4. The retractable wheel assembly of claim 2, wherein the first arm
and third arm are spring loaded to thrust the arm assemblies during
the folding of the wheels during takeoff, and unfolding of the
wheels during landing.
5. The retractable wheel assembly of claim 2, wherein the second
arm moves at a higher speed than the first arm and the third arm to
fold the first arm and second arm during the takeoff and landing of
the aircraft.
6. The retractable wheel assembly of claim 2, wherein each
retraction arm is rigidly held by the threaded shaft during landing
of the aircraft, wherein the retraction arms prevents accidental
folding of the arm assemblies connected to the wheels.
7. The retractable wheel assembly of claim 2, further comprising a
guide way defined by a pair of guide blocks centrally positioned
between the arm assemblies, wherein the threaded shaft is
configured to traverse in the forward and the backward movement
through the guide way.
8. The retractable wheel assembly of claim 2, wherein the guide
blocks prevent a sudden impact movement of the arm assemblies
during take-off or landing.
9. The retractable wheel assembly of claim 2, wherein the wheels
are hingedly connected to the lower frame of the aircraft via a
high strength arm frontally positioned to each wheel and a shock
absorber arm rearwardly positioned to the wheels, to avoid
vibrations of the arm assemblies during operation.
Description
BACKGROUND
[0001] Most modern day vehicles have conventional wheel assemblies
that has not undergone any substantial changes in design. In
general, according to conventional mechanical practices, the wheels
are attached at opposing ends of a drive shaft, suspended by a
strut assembly, and separated by, for example, a sway bar. This is
the general construction of vehicles. But in the case of selective
application of wheels, where wheels were used only when needed,
retractable wheel systems were introduced. The best example of such
retractable wheels is in aircraft design which requires retractable
wheel system for takeoff and landing. The retractable wheel system
also finds further application in utility trailers which are used
for a dual purpose of containment of load, as well as transport of
the load. The transport of the utility trailers require wheels that
can be retracted from a slot beneath the chassis of the utility
trailers.
[0002] Most of the retractable wheel systems used nowadays employ a
complex design which uses high strength materials in high
quantities, which considerably increase the cost of the overall
design of the utility applications. Even aircrafts which use
retractable landing gears make use of light weight high strength
materials which are expensive to manufacture and design. The
accidental folding of landing gears during a landing of the
aircraft is also a matter of concern in the design of landing
gears. Therefore, there is a need for a retractable wheel system
which is simpler in design, cost effective, and will prevent
accidental folding of the landing gear during landing operation of
an aircraft. There is the need for a retractable wheel system which
provide a design where the wheels can be extended to a predefined
span which effectively stabilizes the landing of the aircraft, or
the movement of the utility vehicle.
[0003] Hence, there is a long felt but unresolved need for a
retractable wheel assembly which considerably reduces the cost
involved in designing and manufacturing, as well as provide a
stable solution to prevent the accidental folding of the landing
gear during the landing operation of the aircraft.
SUMMARY OF THE INVENTION
[0004] The retractable wheel assembly for an aircraft disclosed
herein comprises at least two arm assemblies, a pair of wheels, a
retraction arm, and the threaded shaft. The arm assemblies are
hingedly attached to a lower frame of the aircraft, and
symmetrically disposed along the lower frame. Each arm assembly
comprises a first arm hingedly connected to the lower frame, a
second arm hingedly linked to the first arm, and a third arm
hingedly linked to the second arm. Each wheel is hingedly connected
at distal ends of the third arm of each arm assembly, and hingedly
connected to the lower frame. The retraction arm is hingedly
connected to the second arm, and a distal end of the retraction arm
in hinged connection with an end of a threaded shaft. Here, the
threaded shaft is centrally positioned between the two arm
assemblies and perpendicular to the arm assemblies.
[0005] The threaded shaft is configured to be actuated in a
rearward movement where the retraction arm is rearwardly pulled
causing the second arm to unfold the arm assembly outwardly and
deploy the wheels for landing of the aircraft. Then, the threaded
shaft is configured to be actuated in a forward movement where the
retraction arm is pushed forward causing the second arm to fold the
arm assembly inwardly and fold the wheels during takeoff of the
aircraft. In an embodiment, the first arm and third arm are spring
loaded to thrust the arm assemblies during the folding of the
wheels during takeoff, and unfolding of the wheels during landing.
In an embodiment, the second arm moves at a higher speed than the
first arm and the third arm to fold the first arm and second arm
during the takeoff and landing of the aircraft.
[0006] In an embodiment, each retraction arm is rigidly held by the
threaded shaft during landing of the aircraft, where the retraction
arms prevents accidental folding of the arm assemblies connected to
the wheels. In an embodiment, the retractable wheel assembly
further comprises a guide way defined by a pair of guide blocks
centrally positioned between the arm assemblies, where the threaded
shaft is configured to traverse in the forward and the backward
movement through the guide way. In an embodiment, the guide blocks
prevent a sudden impact movement of the arm assemblies during
take-off or landing. In an embodiment, the wheels are hingedly
connected to the lower frame of the aircraft via a high strength
arm frontally positioned to each wheel and a shock absorber arm
rearwardly positioned to the wheels, to avoid vibrations of the arm
assemblies during operation. In an embodiment, the wheels are
configured to be extended across a predefined span via radially
extending the arm assembly, wherein the predefined extension of the
wheels stabilizes the landing of the aircraft.
BRIEF DESCRIPTION OF THE DRAWINGS
[0007] FIG. 1A exemplarily illustrates a rear view of the
retractable wheel assembly.
[0008] FIG. 1B exemplarily illustrates a top view of the
retractable wheel assembly.
[0009] FIG. 2 exemplarily illustrates a rear perspective view of
the right wheel of the retractable wheel assembly.
[0010] FIG. 3 exemplarily illustrates a side perspective view of
the right wheel of the retractable wheel assembly.
[0011] FIG. 4A exemplarily illustrates a top perspective view of a
trailer box in an unfolded condition.
[0012] FIG. 4B exemplarily illustrates a top perspective view of a
trailer box in a folded condition, showing the positioning and
working of the retractable wheel assembly below the trailer
box.
DETAILED DESCRIPTION OF THE INVENTION
[0013] With reference to FIGS. 1A-1B, the retractable wheel
assembly 100 disclosed herein comprises at least two arm assemblies
101, a pair of wheels 105 and 106, a retraction arm 107, and the
threaded shaft 108. The arm assemblies 101 are hingedly attached to
a lower frame 109 of a utility vehicle, and symmetrically disposed
along the lower frame 109. Each arm assembly 101 comprises a first
arm 102 hingedly connected to the lower frame 109, a second arm 103
hingedly linked to the first arm 102, and a third arm 104 hingedly
linked to the second arm 103. Each wheel is hingedly connected at
distal ends 104a, as shown in FIG. 1A, of the third arm 104 of each
arm assembly 101, and hingedly connected to the lower frame 109.
One end 107a of the retraction arm 107 is hingedly connected to the
second arm 103, and a distal end 107b of the retraction arm 107 in
hinged connection with an end 108a of a threaded shaft 108. Here,
the threaded shaft 108 is centrally positioned between the two arm
assemblies 101 and perpendicular to the arm assemblies 101.
[0014] The threaded shaft 108 is configured to be actuated in a
rearward movement where the retraction arm 107 is rearwardly pulled
causing the second arm 103 to unfold the arm assembly 101 outwardly
and deploy the wheels 105 and 106 for motion of the utility
vehicle. Then, the threaded shaft 108 is configured to be actuated
in a forward movement where the retraction arm 107 is pushed
forward causing the second arm 103 to fold the arm assembly 101
inwardly and fold the wheels 105 and 106 when the utility vehicle
is positioned at rest. The description is written based on an
aircraft as the `utility vehicle`, but the scope of the description
does not limit the utility vehicle to aircrafts alone, but any
other utility vehicle which require a retractable wheel assembly
100, for example, utility trailers, utility containers, etc.
[0015] FIG. 1A exemplarily illustrates a rear view of a retractable
wheel assembly 100, and FIG. 1B exemplarily illustrates a top view
of the retractable wheel assembly 100. The retractable wheel
assembly 100 for an aircraft disclosed herein comprises at least
two arm assemblies 101, a pair of wheels 105 and 106, a retraction
arm 107, and the threaded shaft 108. The arm assemblies 101 are
hingedly attached to a lower frame 109 of the aircraft, and
symmetrically disposed along the lower frame 109. Each arm assembly
101 comprises a first arm 102 hingedly connected to the lower frame
109, a second arm 103 hingedly linked to the first arm 102, and a
third arm 104 hingedly linked to the second arm 103. Each wheel is
hingedly connected at distal ends 104a, as shown in FIG. 1A, of the
third arm 104 of each arm assembly 101, and hingedly connected to
the lower frame 109. One end 107a of the retraction arm 107 is
hingedly connected to the second arm 103, and a distal end 107b of
the retraction arm 107 in hinged connection with an end 108a of a
threaded shaft 108. Here, the threaded shaft 108 is centrally
positioned between the two arm assemblies 101 and perpendicular to
the arm assemblies 101.
[0016] The threaded shaft 108 is configured to be actuated in a
rearward movement where the retraction arm 107 is rearwardly pulled
causing the second arm 103 to unfold the arm assembly 101 outwardly
and deploy the wheels 105 and 106 for landing of the aircraft.
Then, the threaded shaft 108 is configured to be actuated in a
forward movement where the retraction arm 107 is pushed forward
causing the second arm 103 to fold the arm assembly 101 inwardly
and fold the wheels 105 and 106 during takeoff of the aircraft. In
an embodiment, the first arm 102 and third arm 104 are spring
loaded to thrust the arm assemblies 101 during the folding of the
wheels 105 and 106 during takeoff, and unfolding of the wheels 105
and 106 during landing. The springs used to load the first arm 102
and the second arm 103 are not overly rigid, but just strengthened
enough to provide a thrust for the first arm 102 and the second arm
103. In an embodiment, the second arm 103 moves at a higher speed
than the first arm 102 and the third arm 104 to fold the first arm
102 and second arm 103 during takeoff and landing of the
aircraft.
[0017] In an embodiment, each retraction arm 107 is rigidly held by
the threaded shaft 108 during landing of the aircraft, where the
retraction arms 107 prevents accidental folding of the arm
assemblies 101 connected to the wheels 105 and 106. Here the
retraction arms 107 and the threaded shaft 108 form an angle and
are stabilized at the landing position, whereby the retractable
wheel assembly 100 is prevented from failing via accidental folding
of the wheels 105 and 106. In an embodiment, the retractable wheel
assembly 100 further comprises a guide way 110 defined by a pair of
guide blocks 111 centrally positioned between the arm assemblies
101, where the threaded shaft 108 is configured to traverse in the
forward and the backward movement through the guide way 110. In an
embodiment, the guide blocks 110 prevent a sudden impact movement
of the arm assemblies 101 during take-off or landing.
[0018] In an embodiment, the wheels 105 and 106 are configured to
be extended across a predefined span via radially extending the arm
assembly 101, wherein the predefined extension of the wheels 105
and 106 stabilize the landing of the aircraft. The guide blocks 111
are positioned at constant predefined angles, to further prevent
any accidental retraction of the retraction arm 107 during landing.
The retraction arm 107 does not change the angle in respect to the
threaded shaft 108 to extend or retract the wheels 105 and 106,
whereas the retraction arm 107 driven by the retraction arm 107
moves forward and backward along the guide way 111, causing a
vertical movement in the second arm 103. In an example, in the case
of design of a retractable wheel assembly 100 for a utility
trailer, the threaded shaft 108 can be obtained from a regular car
jack.
[0019] FIG. 2 exemplarily illustrates a rear perspective view of
the right wheel 106 of the retractable wheel assembly 100. In an
embodiment, the retractable wheel assembly 100 is further
configured to be attached to the lower chassis of utility vehicles
which require retractable wheels 105 and 106, for example, right
wheel 106 as shown in FIG. 2. Therefore, the retractable wheel
assembly 100 for utility vehicles is configured to fit in a
predefined space of, for example, about 120 cms (centimeters) wide,
80 cms long, and 20 cms high. The size of the entire retractable
wheel assembly 100 can also be flexibly varied in the manufacturing
unit depending on the usage in different areas. The size described
here is of a small size or of a regular size which is selected for
utility trailers, and these tires are commercially available for
sale in all tires stores. This retractable wheel assembly 100 is
designed mainly for every application which needs a low cost
landing gear for vehicles with retractable landing gear system. In
an embodiment, the wheels 105 and 106 are hingedly connected to the
lower frame 109 of the aircraft via a high strength arm 112
frontally positioned to each wheel 106 and a shock absorber arm 113
rearwardly positioned to the wheel 106, to avoid vibrations of the
arm assemblies 101 during operation. The high strength arm 112 and
the shock absorber arm 113 are connected by a cross bar 114.
[0020] FIG. 3 exemplarily illustrates a side perspective view of
the right wheel of the retractable wheel assembly 100. Referring to
FIGS. 2, the positioning of the high strength arm 112 frontally to
the wheel 106, and the shock absorber arm 113 rearwardly to the
wheel 106, where both high strength arm 112 and shock absorber arm
113 is connected via the cross bar 114, as shown in this side view
in FIG. 3. In construction of the assembly of wheels 105 and 106,
for example, the tire and hub are assembled into two thick sheet of
aluminum or steel, where the arm assembly 101 is connected to the
inner sheet of the wheels 105 and 106 to avoid vibrations with
variation in the speed of motion. This assembly of wheels 105 and
106 is connected to a very strong arm 112 that allows the folding
of the retractable wheel assembly 100. In an example, retractable
wheel assembly 100 can be opened by removing the outer sheet, in
order to repair a flat tire.
[0021] Referring to FIGS. 4A-4B, FIG. 4A exemplarily illustrates a
top perspective view of a trailer box 400 in an unfolded condition,
and FIG. 4B exemplarily illustrates a top perspective view of a
trailer box 400 in a folded condition, showing the positioning and
working of the retractable wheel assembly 100 below the trailer box
400. The foldable assembly of the trailer box 400 makes it easy to
place the trailer box 400 underneath a car within a parking space,
thereby avoiding consumption of extra space in a parking space that
a regular trailer container would have consumed. In an example, the
retractable wheel assembly 100 is configured to be fitted beneath a
foldable trailer box 400 with an inner surface 401 and four side
walls 402, as shown in FIG. 4A, in the deployed position. When the
four side walls 402 are folded perpendicular to the inner surface
401, and clipped, the trailer box 400 is fully formed. The clipping
of the adjacent side walls is performed via clips 403 which are
inserted into respective slots 404 as shown in the FIG. 4B.
Referring to FIG. 4B, the retractable wheel assembly 100 is
positioned below the trailer box 400 and the retractable wheel
assembly 100 comprises the pair of wheels 105 and 106 which are
configured to be folded or unfolded according to the purpose. The
wheels 105 and 106 are in a horizontal position after being fully
unfolded and the retraction arms 107 are hinged together at a hinge
section 108c common to a threaded shaft 108. The threaded shaft 108
extends outwardly as a towing end 108b for attaching a motor
vehicle.
[0022] The trailer box 400 further comprises a jack assembly 405
attached below the trailer box 400. The jack assembly 400 is
configured to elevate the trailer box 400 to a predefined height.
The jack assembly 405 in general, for example, is driven by a motor
with a spindle, so that the motor rotation will entail the rotation
of the spindle and thus folds or extends the jack assembly 405 to a
completely lowered down position or raised up position of the
trailer box 400. To maintain stability during lifting of such
trailer box 400, the jack assembly 405 comprises bars 406 with
support rollers on the floor, one facing forward and the other
backward, so that in the deployed condition, these support rollers
stable maintenance of the trailer box 400 during lifting.
[0023] The joint 407 positioned on the upper bar 406 of jack
assembly 405 constitutes a passage for the threaded shaft 108. In
operation, when a user a vehicles pulls the towing end 108b of the
threaded shaft 108, the jack assembly 405 expands and raises the
trailer box 400 to a desired height. Simultaneously, since the
threaded shaft 108 passes through the hinge section 108c of the
retractable wheel assembly 100, the retractable wheel assembly 100
is also unfolded to deploy the wheels 105 and 106 downward, and put
into operation, as explained in the embodiment of FIGS. 1A-1B. When
the towing end is pulled inside, the jack assembly 405 is lowered,
and simultaneously the wheels 105 and 106 of the retractable wheel
assembly 100 are also folded, as explained in the embodiment of
FIGS. 1A-1B.
[0024] The foregoing examples have been provided merely for the
purpose of explanation and are in no way to be construed as
limiting of the present concept disclosed herein. While the concept
has been described with reference to various embodiments, it is
understood that the words, which have been used herein, are words
of description and illustration, rather than words of limitation.
Further, although the concept has been described herein with
reference to particular means, materials, and embodiments, the
concept is not intended to be limited to the particulars disclosed
herein; rather, the concept extends to all functionally equivalent
structures, methods and uses, such as are within the scope of the
appended claims. Those skilled in the art, having the benefit of
the teachings of this specification, may affect numerous
modifications thereto and changes may be made without departing
from the scope and spirit of the concept in its aspects.
* * * * *